Modular aerial cargo aerodynamic encasement

ABSTRACT

A modular aerial cargo aerodynamic encasement and a method for modular aviation cargo transport is provided. The aviation cargo aerodynamic encasement comprises a platform having a planar upper surface configured to accept cargo and a lower surface. The lower surface includes two or more ground supports displacing a portion of the platform from contact with a supporting surface. The platform includes two or more load transfer structures. The aviation cargo aerodynamic encasement further comprises a fairing configured to detachably couple to the platform, wherein the fairing, when coupled to the platform, forms an aerodynamic encasement, and wherein the aerodynamic encasement is detachably mountable to an aircraft by the two or more load transfer structures.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application is a continuation of U.S. patent applicationSer. No. 16/845,939 filed 10 Apr. 2020, which relates to and claimsbenefit of priority from U.S. Provisional Application No. 62/832,710filed 11 Apr. 2019 titled “Aerial Cargo Container” which both are herebyincorporated by reference in their entirety for all purposes as if fullyset forth herein.

FIELD OF THE PRESENT DISCLOSURE

The present disclosure relates generally to design of shippingcontainers, and more specifically, to aviation cargo containers forautonomous retrieval and delivery of cargo using aerial vehicles.

BACKGROUND

Cargo comes in all shapes and sizes and with differing degrees ofdelivery priority. Low-priority cargo is predominantly shipped usingcontainer ships for the longest hauls and to a lesser extent usingtrucks and trains. The “modality” of cargo transport refers to the typeof vehicle or vessel involved in the conveyance, for example ship, rail,or truck. “Intermodal” containers that are loaded from one transportvehicle type to another are used for batch movement of shipped articles.An intermodal container is typically a standardized shipping container,designed and built for freight transport, meaning these containers canbe used across different modes of transport without unloading andreloading their cargo. Intermodal containers are primarily used to storeand transport materials and products efficiently and securely in theglobal containerized intermodal freight transport system, but smallernumbers and smaller sizes of intermodal containers are in regional useas well. The use of such a container allows for standardized loading andunloading equipment, efficient stacking, and the realization of manyother cost savings.

Standard sizes and intermodal nature of these containers have greatlyfacilitated and lowered the cost of lower priority cargo. Through thesetechnological innovations, cargo has fewer opportunities for theft,touchpoints of personnel and necessary inspection points. And whileships and trains are the normal means of low priority transportation,air cargo has been slow to adopt an intermodal approach to cargotransportation due to a scaling disparity between aircraft capability,weight, and enclosed volume. Accordingly, cost savings from the use ofintermodal containers have not been realized in aircraft transportationand the cost of air cargo transport remains high in comparison to othermodalities.

New business strategies in logistics (e.g., just-in-time delivery) andglobalization of markets have created a strong demand for fastershipping, which cannot be met by traditional freight modes. Ships,trains, and/or trucks are too slow for contemporary demand, yetinfrastructure, manpower and fuel costs of traditional aviation inhibitlow cost air operations. Air freight needs an intermodal solutioncapable of interoperating with an aircraft and a traditional warehouselogistics environment.

One solution for aerial transportation of cargo is to use smallershipping containers called “Unit Load Devices.” A unit load device(“ULD”) is a pallet or container used to load luggage, freight, and mailon wide-body aircraft and specific narrow-body aircraft. It allows alarge quantity of cargo to be bundled into a single unit. Since thisleads to fewer units to load, it saves ground crews time and effort andhelps prevent delayed flights. Each ULD has its own packing list (ormanifest) so that its contents can be tracked. Unfortunately, ULD's aretypically aircraft design dependent. A ULD suitable for a Boeing 747 maynot be compatible with an Airbus 380.

The existence of exterior cargo containers or pods for aircraft is wellknown but rarely, outside military applications, utilized. In almost allinstances these cargo pods are designed to enhance the internal cargocapability of a specific aircraft. While functional, these types ofcontainers must be carefully fitted and secured to the aircraft and aresemi-permanent in nature. Lacking in both the ULD and exterior cargocontainer models for air cargo transport, however, is the regionaltransportation and delivery of cargo to a final destination or theability to quickly mount, dismount, load or unload. Major airports arelargely designed for passenger transportation. Even in instances inwhich cargo aircraft and passenger aircraft coexist, the facilities arenot optimized for the retrieval and delivery of cargo. Moreover, onceair cargo arrives, especially when a ULD is used, the cargo must beunpacked and then repacked into vehicles for local or regionaltransportation. By comparison, a shipborne intermodal container can andis efficiently removed from a ship and secured immediately on a vehicleor a train for further regional transportation. These inefficienciesdrive up cost and remain a challenge.

Utilization of UAVs to deliver cargo locally has gained wide interestrecently. Conceptually, the versatility and autonomy of UAVs make them alogical system for local cargo delivery. Challenges remain, howeverbefore this vision becomes a reality. Most small UAVs have limited rangeand limited lift ability. While small articles can be carried in smallconventional containers (boxes) over short distances current UAV cargodelivery systems are not yet economically feasible on a large scale noras a system by which to deliver and retrieve cargo over longerdistances. New and larger UAVs/drones continue to be developed butlacking is a standardized intermediate intermodal cargo containeroptimized for air transport and utilization with such UAVs.

What is needed therefore is a new kind of shipping container optimizedfor air transport and capable of being transported by UAVs that can alsointegrate with a warehouse environment. These new aerial cargocontainers must smoothly integrate with the world shipping system thatis based on intermodal containers (pallets, jacks, pallet jacks,forklifts) and must also easily accept/deliver cargo and couple anddecouple with UAVs to enable a quick and reliable UAV cargo deliverysystem. These and other deficiencies of the prior art are resolved byone or more embodiments of the present invention.

Additional advantages and novel features of this invention shall be setforth in part in the description that follows, and in part will becomeapparent to those skilled in the art upon examination of the followingspecification or may be learned by the practice of the invention. Theadvantages of the invention may be realized and attained by means of theinstrumentalities, combinations, compositions, and methods particularlypointed out in the appended claims.

SUMMARY

In one aspect, an aviation cargo aerodynamic encasement is disclosed.The aviation cargo aerodynamic encasement comprises a platform having aplanar upper surface configured to accept cargo and a lower surface. Thelower surface includes two or more ground supports displacing a portionof the platform from contact with a supporting surface. The platformincludes two or more load transfer structures. The aviation cargoaerodynamic encasement further comprises a fairing configured todetachably couple to the platform, wherein the fairing, when coupled tothe platform, forms an aerodynamic encasement, and wherein theaerodynamic encasement is detachably mountable to an aircraft by the twoor more load transfer structures.

In one embodiment, the ground supports are configured to displace thelower surface of the platform away from the supporting surfacesufficient to accept a lifting mechanism.

In one or more embodiments, the planar upper surface includes aplurality of tie down fixtures.

In one or more embodiments, the two or more ground supports areaerodynamically shaped.

In one or more embodiments, the two or more load transfer structuresinclude a guide configured to accept a grasping mechanism.

In one or more embodiments, the grasping mechanism is configured toraise the aerodynamic encasement to the aircraft whereby the aerodynamicencasement is mounted to the aircraft.

In one or more embodiments, the platform includes a honeycomb structure.

In one or more embodiments, the platform includes a corrugatedstructure.

In one or more embodiments, the platform is constructed from aerospacematerial selected from a group consisting of aluminum, titanium, carbonfiber, and composite material.

In one or more embodiments, the fairing includes a front portion and arear portion that join to encase the platform.

In one or more embodiments, the front portion and the rear portion arecoupled to each other and to the platform.

In one or more embodiments, the lower surface of the platform forms anexterior surface of the aerodynamic encasement.

In one or more embodiments, the fairing is configured to withstandaerodynamic forces exerted on the aerodynamic encasement up to 300 mph.

In one or more embodiments, the fairing is a singular componentconfigured to cover the platform.

In one or more embodiments, the fairing includes a detachable side panelconfigured to laterally accept the platform to form the aerodynamicencasement.

In another aspect, a method for modular aviation cargo transport isdisclosed. The method comprises loading a platform with cargo, theplatform having a planar upper surface configured to accept the cargoand a lower surface wherein the lower surface includes two or moreground supports displacing a portion of the platform from contact with asupporting surface and wherein the platform includes two or more loadtransfer structures. The method further comprises encasing the platformwith a fairing, the fairing configured to detachably couple to theplatform wherein the fairing, when coupled to the platform, forms anaerodynamic encasement. The method further comprises detachably mountingthe aerodynamic encasement to an aircraft by the two or more loadtransfer structures.

In one or more embodiments, the method further comprises displacing, bythe ground supports, the lower surface of the platform away thesupporting surface sufficient to accept a lifting mechanism.

In one or more embodiments, the method further comprises accepting, bythe two or more load transfer structures, a grasping mechanism whereinthe grasping mechanism is configured to raise the aerodynamic encasementto the aircraft.

In one or more embodiments, the method further comprises mounting theaerodynamic encasement to the aircraft.

In one or more embodiments, the fairing includes a front portion and arear portion and further comprising joining the front portion to therear portion to encase the platform.

In one or more embodiments, responsive to joining the front portion andthe rear portion, the method further comprises coupling the fairing tothe platform.

In one or more embodiments, the lower surface of the platform forms anexterior surface of the aerodynamic encasement.

In one or more embodiments, the fairing is a singular componentconfigured to cover the platform.

In one or more embodiments, the method further comprises detaching adetachable side panel from the fairing.

In one or more embodiments, the method further comprises laterallyaccepting the platform into the fairing and reattaching the detachableside panel to form the aerodynamic encasement.

The features and advantages described in this disclosure and in thefollowing detailed description are not all-inclusive. Many additionalfeatures and advantages will be apparent to one of ordinary skill in therelevant art in view of the drawings, specification, and claims hereof.Moreover, it should be noted that the language used in the specificationhas been principally selected for readability and instructional purposesand may not have been selected to delineate or circumscribe theinventive subject matter; reference to the claims is necessary todetermine such inventive subject matter.

BRIEF DESCRIPTION OF THE DRAWINGS

For a more complete understanding of example embodiments of the presentdisclosure, reference is now made to the following descriptions taken inconnection with the accompanying drawings in which:

FIGS. 1A-1D illustrate diagrammatic views of an aviation cargoaerodynamic encasement, in accordance with an example embodiment of thepresent disclosure;

FIG. 2 illustrates a diagrammatic perspective view of a platform of theaerodynamic encasement of FIG. 1, in accordance with one or moreembodiments of the present disclosure;

FIG. 3 illustrates a diagrammatic side view of a fairing of theaerodynamic encasement of FIG. 1, in accordance with one or moreembodiments of the present disclosure;

FIG. 4 illustrates a diagrammatic cross-section view of the fairing ofFIG. 3;

FIGS. 5A-5B illustrate diagrammatic side and top planar viewsrespectively of the platform in loaded configurations, in accordancewith one or more embodiments of the present disclosure;

FIGS. 6A-6B illustrate diagrammatic views of tie down fixtures for theplatform, in accordance with one or more embodiments of the presentdisclosure;

FIGS. 7A-7C illustrate various exemplary design configurations for theplatform, in accordance with one or more embodiments of the presentdisclosure;

FIG. 8 illustrates a diagrammatic exploded view of the aerodynamicencasement showing relative arrangement of the platform and the fairingthereof, in accordance with one or more embodiments of the presentdisclosure;

FIG. 9 illustrates a diagrammatic sectioned view of the aerodynamicencasement, in accordance with one or more embodiments of the presentdisclosure;

FIGS. 10A-10C illustrate various exemplary design configurations for theaerodynamic encasement with load transfer structures, in accordance withone or more embodiments of the present disclosure;

FIG. 11 depicts an exemplary implementation of the aerodynamicencasement being coupled to an aircraft, in accordance with one or moreembodiments of the present disclosure;

FIG. 12 depicts an exemplary implementation of the aerodynamicencasement being loaded, in accordance with one or more embodiments ofthe present disclosure;

FIG. 13A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with another embodiment of the presentdisclosure;

FIG. 13B depicts an exemplary implementation of the aerodynamicencasement of FIG. 13A for loading thereof;

FIG. 14A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 14B depicts an exemplary implementation of the aerodynamicencasement of FIG. 14A for loading thereof;

FIG. 15A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 15B depicts an exemplary implementation of the aerodynamicencasement of FIG. 15A for loading thereof;

FIG. 16A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 16B depicts an exemplary implementation of the aerodynamicencasement of FIG. 16A for loading thereof;

FIG. 17A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 17B depicts an exemplary implementation of the aerodynamicencasement of FIG. 17A for loading thereof;

FIG. 18A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 18B depicts an exemplary implementation of the aerodynamicencasement of FIG. 18A for loading thereof;

FIG. 19A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 19B depicts an exemplary implementation of the aerodynamicencasement of FIG. 19A for loading thereof;

FIG. 20A illustrates a diagrammatic perspective view of the aerodynamicencasement, in accordance with yet another embodiment of the presentdisclosure;

FIG. 20B depicts an exemplary implementation of the aerodynamicencasement of FIG. 20A for loading thereof;

FIG. 21 illustrates a schematic diagram of the aerodynamic encasement,in accordance with one or more embodiments of the present disclosure;

FIG. 22 illustrates a schematic diagram of the aerodynamic encasement,in accordance with one or more embodiments of the present disclosure;and

FIG. 23 illustrate a flowchart listing steps involved in a method formodular aviation cargo transport, in accordance with various embodimentsof the present disclosure.

The Figures depict embodiments of the present invention for purposes ofillustration only. One skilled in the art will readily recognize fromthe following discussion that alternative embodiments of the structuresand methods illustrated herein may be employed without departing fromthe principles of the invention described herein.

DETAILED DESCRIPTION

An aviation cargo aerodynamic encasement and a method for modularaviation cargo transport are hereafter described by way of example. Theaviation cargo aerodynamic encasement of the present invention comprisesa platform having a planar upper surface configured to accept cargo anda lower surface. The lower surface includes two or more ground supportsdisplacing a portion of the platform from contact with a supportingsurface. The platform further includes two or more load transferstructures. A fairing is configured to detachably couple to theplatform, wherein the fairing, when coupled to the platform, forms anaerodynamic encasement. The newly formed aerodynamic encasement isthereafter detachably mountable to an aircraft by the two or more loadtransfer structures.

In the following description, for purposes of explanation, numerousspecific details are set forth in order to provide a thoroughunderstanding of the present disclosure. It will be apparent, however,to one skilled in the art that the present disclosure can be practicedwithout these specific details. In other instances, apparatuses andmethods are shown in block diagram form only in order to avoid obscuringthe present disclosure.

Embodiments of the present invention are hereafter described in detailwith reference to the accompanying Figures. Although the invention hasbeen described and illustrated with a certain degree of particularity,it is understood that the present disclosure has been made only by wayof example and that numerous changes in the combination and arrangementof parts can be resorted to by those skilled in the art withoutdeparting from the spirit and scope of the invention.

The following description with reference to the accompanying drawings isprovided to assist in a comprehensive understanding of exemplaryembodiments of the present invention as defined by the claims and theirequivalents. It includes various specific details to assist in thatunderstanding but these are to be regarded as merely exemplary.Accordingly, those of ordinary skill in the art will recognize thatvarious changes and modifications of the embodiments described hereincan be made without departing from the scope and spirit of theinvention. Also, descriptions of well-known functions and constructionsare omitted for clarity and conciseness.

The terms and words used in the following description and claims are notlimited to the bibliographical meanings, but, are merely used by theinventor to enable a clear and consistent understanding of theinvention. Accordingly, it should be apparent to those skilled in theart that the following description of exemplary embodiments of thepresent invention are provided for illustration purpose only and not forthe purpose of limiting the invention as defined by the appended claimsand their equivalents.

By the term “substantially” it is meant that the recited characteristic,parameter, or value need not be achieved exactly, but that deviations orvariations, including for example, tolerances, measurement error,measurement accuracy limitations and other factors known to those ofskill in the art, may occur in amounts that do not preclude the effectthe characteristic was intended to provide.

Like numbers refer to like elements throughout. In the figures, thesizes of certain lines, layers, components, elements or features may beexaggerated for clarity.

The terminology used herein is for the purpose of describing particularembodiments only and is not intended to be limiting of the invention. Asused herein, the singular forms “a,” “an” and “the” are intended toinclude the plural forms as well, unless the context clearly indicatesotherwise. Thus, for example, a reference to “a component surface”includes reference to one or more of such surfaces.

As used herein any reference to “one embodiment” or “an embodiment”means that a particular element, feature, structure, or characteristicdescribed in connection with the embodiment is included in at least oneembodiment. The appearances of the phrase “in one embodiment” in variousplaces in the specification are not necessarily all referring to thesame embodiment.

As used herein, the terms “comprises,” “comprising,” “includes,”“including,” “has,” “having” or any other variation thereof, areintended to cover a non-exclusive inclusion. For example, a process,method, article, or apparatus that comprises a list of elements is notnecessarily limited to only those elements but may include otherelements not expressly listed or inherent to such process, method,article, or apparatus. Further, unless expressly stated to the contrary,“or” refers to an inclusive or and not to an exclusive or. For example,a condition A or B is satisfied by any one of the following: A is true(or present) and B is false (or not present), A is false (or notpresent) and B is true (or present), and both A and B are true (orpresent).

Unless otherwise defined, all terms (including technical and scientificterms) used herein have the same meaning as commonly understood by oneof ordinary skill in the art to which this invention belongs. It will befurther understood that terms, such as those defined in commonly useddictionaries, should be interpreted as having a meaning that isconsistent with their meaning in the context of the specification andrelevant art and should not be interpreted in an idealized or overlyformal sense unless expressly so defined herein. Well-known functions orconstructions may not be described in detail for brevity and/or clarity.

It will be also understood that when an element is referred to as being“on,” “attached” to, “connected” to, “coupled” with, “contacting”,“mounted” etc., another element, it can be directly on, attached to,connected to, coupled with or contacting the other element orintervening elements may also be present. In contrast, when an elementis referred to as being, for example, “directly on,” “directly attached”to, “directly connected” to, “directly coupled” with or “directlycontacting” another element, there are no intervening elements present.It will also be appreciated by those of reasonable skill in the relevantart that references to a structure or a feature that is “adjacent” toanother feature may have portions that overlap or underlie that feature.

Spatially relative terms, such as “under,” “below,” “lower,” “over,”“upper” and the like, may be used herein for ease of description todescribe one element or feature's relationship to another element(s) orfeature(s) as illustrated in the figures. It will be understood that thespatially relative terms are intended to encompass differentorientations of a device in use or operation in addition to theorientation depicted in the figures. For example, if a device in thefigures is inverted, elements described as “under” or “beneath” otherelements or features would then be oriented “over” the other elements orfeatures. Thus, the exemplary term “under” can encompass both anorientation of “over” and “under”. The device may be otherwise oriented(rotated 90 degrees or at other orientations) and the spatially relativedescriptors used herein interpreted accordingly. Similarly, the terms“upwardly,” “downwardly,” “vertical,” “horizontal” and the like are usedherein for the purpose of explanation only unless specifically indicatedotherwise.

Included in the description are flowcharts depicting examples of themethodology which may be used in conjunction with an aerial cargoaerodynamic encasement as well as load and reposition the cargoaerodynamic encasement relative to a vehicle. In the followingdescription, it will be understood that each block of the flowchartillustrations, and combinations of blocks in the flowchartillustrations, can be implemented by computer program instructions incombination with physical components. These computer programinstructions may be loaded onto a computer or other programmableapparatus to produce a machine such that the instructions that executeon the computer or other programmable apparatus create means forimplementing the functions specified in the flowchart block or blocks.These computer program instructions may also be stored in acomputer-readable memory that can direct a computer or otherprogrammable apparatus to function in a particular manner such that theinstructions stored in the computer-readable memory produce an articleof manufacture including instruction means that implement the functionspecified in the flowchart block or blocks. The computer programinstructions may also be loaded onto a computer or other programmableapparatus to cause a series of operational steps to be performed in thecomputer or on the other programmable apparatus to produce a computerimplemented process such that the instructions that execute on thecomputer or other programmable apparatus provide steps for implementingthe functions specified in the flowchart block or blocks.

Accordingly, blocks of the flowchart illustrations support combinationsof means for performing the specified functions and combinations ofsteps for performing the specified functions. It will also be understoodthat each block of the flowchart illustrations, and combinations ofblocks in the flowchart illustrations, can be implemented by specialpurpose hardware and/or computer systems that perform the specifiedfunctions or steps, or combinations of special purpose hardware andcomputer instructions.

Some portions of this specification are presented in terms of algorithmsor symbolic representations of operations on data stored as bits orbinary digital signals within a machine memory (e.g., a computermemory). These algorithms or symbolic representations are examples oftechniques used by those of ordinary skill in the data processing artsto convey the substance of their work to others skilled in the art. Asused herein, an “algorithm” is a self-consistent sequence of operationsor similar processing leading to a desired result. In this context,algorithms and operations involve the manipulation of informationelements. Typically, but not necessarily, such elements may take theform of electrical, magnetic, or optical signals capable of beingstored, accessed, transferred, combined, compared, or otherwisemanipulated by a machine. It is convenient at times, principally forreasons of common usage, to refer to such signals using words such as“data,” “content,” “bits,” “values,” “elements,” “symbols,”“characters,” “terms,” “numbers,” “numerals,” “words”, or the like.These specific words, however, are merely convenient labels and are tobe associated with appropriate information elements.

Unless specifically stated otherwise, discussions herein using wordssuch as “processing,” “computing,” “calculating,” “determining,”“presenting,” “displaying,” or the like may refer to actions orprocesses of a machine (e.g., a computer) that manipulates or transformsdata represented as physical (e.g., electronic, magnetic, or optical)quantities within one or more memories (e.g., volatile memory,non-volatile memory, or a combination thereof), registers, or othermachine components that receive, store, transmit, or displayinformation.

Upon reading this disclosure, those of skill in the art will appreciatestill additional alternative structural and functional designs for asystem and a process for autonomous retrieval and delivery of cargoaerodynamic encasements through the disclosed principles herein. Thus,while particular embodiments and applications have been illustrated anddescribed, it is to be understood that the disclosed embodiments are notlimited to the precise construction and components disclosed herein.Various modifications, changes and variations, which will be apparent tothose skilled in the art, may be made in the arrangement, operation anddetails of the method and apparatus disclosed herein without departingfrom the spirit and scope of the invention.

According to embodiments of the present invention, an aviation cargoaerodynamic encasement (hereinafter, sometimes referred simply to as“aerodynamic encasement”) suitable for long distance aerial transport,including by unmanned aerial vehicles (UAVs), is hereafter disclosed byway of example. The aviation cargo aerodynamic encasement of the presentinvention is the aerial counterpart to intermodal shipping aerodynamicencasements. The morphology, material composition, and attachment pointsare of necessity unique for the disclosed aerodynamic encasement as isits ability to track its location and communicate to an overall cargomanagement system. In one example, the present invention provides asubstantially rectangular shape aerodynamic encasement optimized forexternal air transport while nonetheless compatible with intermodalaerodynamic encasements. In one embodiment, the disclosed aerodynamicencasements are stackable to facilitate pre-loading and transportationto and from a port of call while maintaining their ability to integratewith aerial vehicles. Moreover, the aerodynamic encasements are modularin that they comprise a platform that is easily loaded which can then beconfigured with a fairing encapsulating the platform with an aerodynamicshape suitable for transport mounted to the exterior of an aircraft. Thecomposition of the aerodynamic encasements, platform and fairing, islightweight yet strong enough to support several hundred pounds ofcargo.

Referring to the accompanied drawings, FIGS. 1A-1B illustratediagrammatic views of an aviation cargo aerodynamic encasement(generally referred by the numeral 100), in accordance with one or moreembodiments of the present disclosure. The aerodynamic encasement 100 isgenerally crafted with a contoured, aerodynamic shape having a nose 102and tail 104 in order to reduce aerodynamic drag upon the aerodynamicencasement 100 while mounted to an aerial vehicle. In some embodiments,the nose 102 and tail 104 are removable components. Removing thesecomponents results in a substantially rectangular shaped aerodynamicencasement 100. Generally, the length, width and depth of theaerodynamic encasement 100 is optimized for use with UAVs and fortransport within existing intermodal aerodynamic encasements. In oneembodiment, the dimensions of the aerodynamic encasement 100 areoptimized for carrying loaded standard pallets.

The construction of the aerodynamic encasement 100 is suited for airoperations with low weight and high strength being primary designconsiderations. In one embodiment, the aerodynamic encasement 100 has acomposite construction (e.g. carbon fiber and epoxy). An alternativeembodiment may use another process or material to navigate the tradeoffsbetween weight, strength and cost for the aerodynamic encasement 100.Indeed, there may be multiple types of construction while maintainingthe same size and UAV compatibility. For example, a cheaper and lessdurable (or instead compostable/burnable) version may be used formissions in which it is unlikely the aerodynamic encasement 100 will bereused or in which the useful life of the aerodynamic encasement is ofminimal concern (supply of combat troops in the field, for example).Other embodiments may include a more robust, durable construction methodto manufacture the aerodynamic encasement 100 that will be used multipletimes and thus need to be robust. In one or more embodiments, theaerodynamic encasement 100 can be stacked and loaded into an intermodalaerodynamic encasement whereby physical features of each aerodynamicencasement 100 interlock with other features, allowing the aerodynamicencasements 100 stack vertically on each other.

According to embodiments of the present invention, as may be seen fromFIG. 1B, the aerodynamic encasement 100 includes a platform 106. In oneversion of the present invention the platform 106 forms the floor of theaerodynamic encasement 100. FIG. 2 illustrates a diagrammatic view ofthe platform 106, in accordance with an embodiment of the presentdisclosure. The platform 106 is shown to have a generally rectangularshape; however, in other examples, the platform 106 may have any othersuitable shape, such as square or the like, without departing from thescope of the present invention. The platform 106 includes an uppersurface 108 and a lower surface 110 (the lower surface 110 beinggenerally shown herein). Herein, the upper surface 108 is a planarsurface. The upper surface 108 is configured to accept cargo, asdiscussed later in more detail. In one embodiment of the presentinvention, the height between the bottom of the ground supports 112 andthe bottom of the platform 110 in FIG. 2, is chosen to work with palletjacks—i.e. high enough so that a pallet jack 114 in its lower positioncan slip forks under the platform 106, and low enough that the groundsupports 112 clear the ground when the pallet jack 114 is in its raisedposition.

Further, as illustrated, the lower surface 110 includes two or moreground supports 112. In the present illustration, the lower surface 110has been shown to have four ground supports 112. The ground supports 112displaces, at least, a portion of the platform from contact with asupporting surface, such as the ground on which the platform 106 isplaced. As depicted in FIG. 2, the ground supports 112 are configured todisplace the lower surface 110 of the platform 106 away from thesupporting surface (i.e. the ground) sufficient to accept a liftingmechanism, such as an exemplary lifting mechanism 114 as shown. It maybe appreciated that the lifting mechanism 114 may be a forklift or thelike, with the forks thereof being placed accepted under the platform106 for lifting thereof, as and when required. In the presentembodiments, the two or more ground supports 112 are aerodynamicallyshaped. Such aerodynamic shape of the ground supports 112 helps toreduce aerodynamic drag upon the aerodynamic encasement 100 whilemounted to an aerial vehicle (also interchangeably referred to as“aircraft” without any limitations).

Referring back to FIG. 1B, the aerodynamic encasement 100 also includesa fairing 116. FIG. 3 illustrates a diagrammatic view of the fairing116, in accordance with an embodiment of the present invention. Asillustrated in FIG. 3, the fairing 116 has a generally nose-cone shape.Such shape helps to reduce aerodynamic drag upon the aerodynamicencasement 100 while mounted to an aerial vehicle. In particular, thefairing 116, in one embodiment, includes a front portion 118 and a rearportion 120. In the present examples, the front portion 118 may formnose 102 of the aerodynamic encasement 100 and the rear portion 120 mayinclude tail 104 of the aerodynamic encasement 100. The front portion118 and the rear portion 120 are joined together to complete the fairing116. When joined, the front portion 118 and the rear portion 120 of thefairing 116 encase the platform 106. Specifically, the front portion 118and the rear portion 120 of the fairing 116 are coupled to each otherand to the platform 106. As illustrated, the fairing 116 may alsoinclude legs 122 complementary to the ground supports 112 in theplatform 106.

In general, the fairing 116 is configured to detachably couple to theplatform 106. As shown in FIG. 4, it may be understood that the fairing116 may have a generally circular cross-section with a section towardsthe lower part being cut-off in order to be able to couple to theplatform 106. In other embodiments the cross-section may be morerectangular to facilitate intermodal incorporation. For this purpose, asillustrated in FIG. 2, the platform 106 includes channels 126 formedtherein. Further, the fairing 116 may include corresponding channels(not shown) at the inside region of edges 128 of the cut-off circularcross-section of the fairing 116. The channels 126 in the platform 106may engage with the corresponding channels 128 in the fairing 116 toconfigure the fairing 116 to detachably couple to the platform 106.Other methodology to couple the fairing 116 to the platform 106 to formthe aerodynamic encasement are contemplated and will be recognized byone or reasonable skill in the relevant art. The fairing 116, whencoupled to the platform 106, forms an aerodynamic encasement. With sucha design configuration, it shall be understood that the lower surface110 of the platform 106 forms an exterior surface of the aerodynamicencasement. In the present embodiment, the aerodynamic encasement 100 isimplemented to be mounted to an exterior of an aircraft (as discussedlater) as an encased platform. Therefore, the aerodynamic encasement 100may be subjected to many forces while mounted to an aerial vehicle. Insuch an embodiment, the fairing 116 is configured to withstandaerodynamic forces exerted on the aerodynamic encasement up to, forexample, 300 mph as well as typical accelerations forces encounteredduring flight operations. Other embodiments may include fairings havinghigher structural integrity to withstand increased dynamic loading.Further, in another embodiment, the fairing 116 may be a singularcomponent configured to cover the entirety of the platform 106.

As discussed, in the present embodiments, the upper surface 108 of theplatform 106 is configured to accept cargo. For this purpose, asillustrated in FIGS. 5A-5B, the planar upper surface 108 includes aplurality of tie down fixtures 130. The tie down fixture 130 (also knownas a tie down strap, a ratchet strap, a lashing strap, fittings)includes a fastener used to hold down cargo or equipment duringtransport on the platform 106. The tie down fixtures 130 are, in oneembodiment, essentially webbing outfitted with tie down hardwareattachable to the area surrounding the cargo or equipment, loop over thecargo or equipment, and/or attach to the cargo or equipment. FIGS. 6Aand 6B illustrate two exemplary types of tie down fixtures 130 that maybe employed for the embodiments of the present disclosure. For example,FIG. 6A provides a tie down fixture 130 with a variety of loop straps,which includes a single piece of webbing that is looped around the itemto be protected and the two endpoints are brought together at the tiedown fastener for fastening and providing tension. Herein, the tie downprovisions (fittings) may be made using L-track. FIG. 6B provides a tiedown fixture 130 with pass-through design, as known in the art. Again,as illustrated in FIGS. 5A-5B, the cargo (herein shown in the form ofdashed boxes) may be placed over the upper surface 108 of the platform106, and the tie down fixtures 130 are used to secure and hold down thecargo on the platform 106. The use of tie down fixtures 130 allows tosecure different type and sizes of cargos on the platform 106, asrequired.

In one embodiment, the aerodynamic encasement 100 may include one ormore bladders (not shown) that can be inflated to fill empty space. Suchinflated bladders can fill areas of the aerodynamic encasement 100 thatare not used and/or can be used in lieu of the tie down fixtures 130. Inone embodiment, these bladders are positioned on the sides of theaerodynamic encasement 100. The bladders can optionally include apressure release system to adjust for external pressure changes incurredduring flight operations. In other alternative embodiments, the bladderscan store fuel for the aerial vehicle or even as a product fortransportation. Such fuel-storage bladders can be rigid with bafflesand/or can employ open-cell foam to prevent fuel sloshing, as may becontemplated by a person skilled in the art with racing fuel tanks.

In one example, as illustrated, the encasement may also include one ormore payload dividers 138 for separating the cargo for uniform loadingof the platform 106, as discussed later in more detail. That is, theinternal compartments of the aerodynamic encasement 100 may includeinternal payload dividers 138 that can be repositioned to ensure thatloads do not shift and damage cargo, pod, or the aircraft fuselage oraffect the center of gravity (“CG”) of the aerial vehicle during flightoperations. These payload dividers 138, in one embodiment, can befastened at 3 points and/or can also act as a lateral reinforcement forthe aerodynamic encasement 100. The internal payload dividers 138 of thepresent invention are designed to resist lateral and negative G forceswith the bottom structure of the aerodynamic encasement 100 and towithstand positive G-forces experienced during flight and hard landings.The payload dividers 138 are adjustable to accommodate different sizesof cargo. Alternatively, the opening of the aerodynamic encasement 100can be an open span with one or more removable bars that spans thisopening, serving as lateral reinforcement. In another embodiment, cargocan be secured within the aerodynamic encasement 100 by bracing thecargo against a panel which is set into the aerodynamic encasement 100to function as an internal divider or using a net/webbing. Webbing canbe integrated with the internal panel dividers 138. Cargo can also besecured with a sub-sack system having gear loops for tie-down. Gear issecured in the bag, and then the bag is secured to cargo aerodynamicencasement. Sub sacks can be integrated with internal panel dividers138. In an embodiment, the locations of the tie down fixtures 130 areintegrated with each panel divider 138 and on the sidewalls of theaerodynamic encasement 100 to prevent further movement of the cargo.

According to embodiments of the present disclosure, the platform 106 mayhave different structural configurations or designs to support the cargothereon. In one embodiment, as illustrated in FIG. 7A, the platform 106,or specifically the upper surface 108 of the platform 106, includes ahoneycomb structure. In another embodiment, as illustrated in FIG. 7B,the platform 106, or specifically the upper surface 108 of the platform106, includes a corrugated structure. In yet another embodiment, asillustrated in FIG. 7C, the platform 106, or specifically the uppersurface 108 of the platform 106, includes a laminated structure. It maybe contemplated that the structural configuration or design choice forthe platform 106 may be based on the type of cargo to be supported onthe platform 106. Further, in an embodiment, the platform 106 isconstructed from aerospace material selected from a group consisting ofaluminum, titanium, carbon fiber, and composite material. Such materialchoice provides strong yet light-weight platform 106 to allow for easyand cost-efficient aerial travel.

FIG. 8 illustrates an exploded diagrammatic view of the aerodynamicencasement 100 (or specifically the encasement), in accordance with anembodiment of the present invention. As illustrated, the aerodynamicencasement 100 includes the platform 106 and the fairing 116. Herein,the platform 106 includes two or more load transfer structures 132. Theload transfer structures 132 may generally be in the form of extensionsfrom the upper surface 108 of the platform 106. FIG. 8 provides anembodiment of aerodynamic encasement 100 with the platform 106 havingthe load transfer structures 132 with a simple (conceptual) design. FIG.9A provides a sectioned (or cut-away) view of the aerodynamic encasement100 with the platform 106 having the load transfer structures 132, inaccordance with embodiments of the present invention. As illustrated,the load transfer structures 132 include pairs of guides 124, 134configured to accept a grasping mechanism (not shown). It shall beunderstood that the grasping mechanism is configured to raise (or lower)the aerodynamic encasement to the aircraft whereby the aerodynamicencasement is mounted to the aircraft using various latching points 136.In an embodiment, as shown, the guides 124,134 may be in the form ofguide bars (as shown). The load transfer structures 132 incorporate thelatching points 136 to enable direct load transfer to the aircraft oncemounted. FIGS. 10A-10C illustrates different views of the aerodynamicencasement 100 (or the encasement) with alternative load transferstructures 132, in accordance with the embodiments of the presentinvention.

In a preferred embodiment, the aerodynamic encasement 100 is coupled tothe underside of an aerial vehicle's fuselage. In other embodiments,multiple aerodynamic encasements 100 can be mounted under the fuselageand/or at various locations under wing depending on the capability ofthe aerial vehicle. In still other embodiments, the aerodynamicencasement 100 is capable of being partially or entirely drawn into thefuselage of the aerial vehicle or mounted securely on top of thevehicle. In one embodiment, a compressible gasket along the upper edgeof the cargo aerodynamic encasement comprises a seal with thecorresponding surface of the aircraft. In one embodiment, a compressiblegasket along the upper edge of the aerodynamic encasement 100 includes aseal with the corresponding surface of the aircraft fuselage. In analternate embodiment, the seal to which the interfaces of theaerodynamic encasement 100 are embedded in the belly of the fuselage. Inthe case in which the aerodynamic encasement 100 couples to theunderside of an aerial vehicle's fuselage, this seal keeps dust,moisture and other particles from entering the aerodynamic encasementduring flight operations and prevents the aerodynamic encasement 100from abrading the fuselage.

In the present embodiments, the aerodynamic encasement 100 (or theaerodynamic encasement) is detachably mountable to an aircraft 137 (i.e.an aerial vehicle like UAV) by the two or more load transfer structures132 in conjunction with a plurality of latching points 136. FIG. 11depicts an exemplary implementation showing the encasement (herein, onlythe platform 106 with the load transfer structures 132 is shown forsimplicity sake) being mounted to an aircraft 10 (schematically shown).As may be seen, some cords 12 may be hung from the aircraft 10 which maybe coupled to the load transfer structures 132 and the aerodynamicencasement 100 is pulled towards the aircraft 10 to be mounted therewithby any suitable coupling mechanism known in the art without anylimitations. In another example, the platform 106 may have a winch (notshown) or the like providing cord to be attached to a support structurein the aircraft, such that the encasement may be pulled towards theaircraft for mounting therewith.

A significant feature of the present invention is the modular nature ofthe aerodynamic encasement 100 and its ability to couple with an aerialvehicle. This coupling is accomplished through a series of steps whichprogressively align and draw together the aerodynamic encasement 100 tothe fuselage. The aerodynamic encasement 100 contains guidance featureswhich join with a grasping mechanism from the aircraft to place theaerodynamic encasement 100 into correct alignment and position forcoupling with the aircraft. These guidance features can be removable forstacking and transport. Fundamentally the guidance feature of eachaerodynamic encasement 100 guides the grasping mechanism of the UAV intoalignment along the longitudinal center axis of the aerodynamicencasement 100. As the grasping mechanism engages the aerodynamicencasement 100, the longitudinal center axis of the aerodynamicencasement 100 becomes parallel to the longitudinal axis of theaircraft. Guidance features for this grasping are mounted in the nose102 and the tail 104 of each aerodynamic encasement 100. In analternative embodiment, they are mounted to structural spreader barslocated at each end and in the interior of the aerodynamic encasement100. In some embodiments, the guidance features are standaloneassemblies dropped into each aerodynamic encasement 100 with a pluralityof fasteners. With locations to catch each fastener present on the sidesand ends of the aerodynamic encasement 100, the guidance featureassembly is easily installed.

FIG. 12 depicts a process of loading the cargo in the aerodynamicencasement 100, in accordance with an exemplary embodiment of thepresent invention. As may be seen, the cargo (herein, shown as boxes) isfirst loaded onto the platform 106. Then, the front portion 118 and therear portion 120 of the fairing 116 are moved towards each other, andthat the front portion 118 and the rear portion 120 join together toencase the platform 106. It may be appreciated that the front portion118 and the rear portion 120 may have seals for secure joining of thetwo portions 118, 120, so as to protect the cargo therein while theaerodynamic encasement 100 is mounted to an aerial vehicle. It may alsobe appreciated that the platform 106 with the ground supports 112 allowsfor easy sliding of the two portions 118, 120, along the channels 126,without the need of lifting the platform 106 above the support surface.

FIGS. 13A-13B illustrate the aviation cargo aerodynamic encasement 100,in accordance with another embodiment of the present disclosure. Herein,the fairing 116 includes a side panel 140 provided on a lateral side ofthe fairing 116. The side panel 140 is configured to laterally acceptthe platform 106 to form the aerodynamic encasement. Herein, as may beseen from FIG. 13B, the platform 106 is loaded from the lateral side ofthe fairing 116 through the side panel 140. In one or more embodiments,the side panel 140 is a detachable side panel. In such case, forloading, the detachable side panel 140 is detached from the fairing 116,the platform 106 is laterally accepted into the fairing 116, and finallythe detachable side panel 140 is reattached to form the aerodynamicencasement. In other embodiments, the side panel 140 may be in the formof hinged door or any other suitable configuration to provide access tothe inside of the aerodynamic encasement 100 (i.e. encasement) withoutdeparting from the scope and the spirit of the present invention.Sensors can, in other embodiments of the present invention, beincorporated to identify whether (and when) the doors and/or componentsof the fairing are secure. For example should the door come open inflight or when the interior of the aerodynamic encasement 100 wasaccessed on the ground.

FIGS. 14A-14B illustrate the aviation cargo aerodynamic encasement 100,in accordance with another embodiment of the present disclosure. Herein,the fairing 116 has an opening on a side thereof from which the platform106 may be loaded. FIGS. 15A-15B illustrate the aviation cargoaerodynamic encasement 100, in accordance with yet another embodiment ofthe present disclosure. Herein, the fairing 116 may be formed of twosections which may be hinged together, so as to be disposed between anopen position to allow loading of the platform and a closed position toform the aerodynamic encasement. FIGS. 16A-16B illustrate the aviationcargo aerodynamic encasement 100, in accordance with yet anotherembodiment of the present disclosure. Herein, the fairing 116 may havetwo front sections hinged at ends of a larger back section, in which thetwo sections can be disposed in respective open positions to allowloading of the platform and their closed positions to form theaerodynamic encasement. FIGS. 17A-17B illustrate the aviation cargoaerodynamic encasement 100, in accordance with yet another embodiment ofthe present disclosure. Herein, the fairing 116 may have two sectionswhich may be pivoted opposite to each other to provide space forreceiving the platform 106 and may be pivoted back towards each other toform the encasement. Herein, an upper section of the fairing 116 may bepivotally coupled with a lower section thereof, such that the said uppersection may be pivoted (lifted up) to allow for receiving of theplatform 106 and again pivoted back (pushed down) to form theencasement. FIGS. 18A-18B and FIGS. 19A-19B illustrate the aviationcargo aerodynamic encasement 100, in accordance with yet anotherembodiment of the present disclosure. Herein, the fairing may providevertical support structures between which the platform 106 is supported,and the fairing 116 is covered by another structure to form theencasement. FIGS. 20A-20B illustrate the aviation cargo aerodynamicencasement 100, in accordance with yet another embodiment of the presentdisclosure. Herein, the fairing 116 is in the form of a bag with a ziplike fastener which may be opened to allow receiving of the platform 106and closed to form the encasement. A hard-shell fairing as previouslydescribed would thereafter encase the bag forming the encasement.

In one or more embodiments, the aerodynamic encasement 100 of thepresent invention may include communication and networking systems thatenable the aerodynamic encasement 100 to determine its location and tocommunicate that location to a central management facility/softwaresystem and/or a nearby UAV or ground/warehouse crew. In one embodiment,the aerodynamic encasement includes the ability to gain its geographiclocation using satellite-based positioning systems. In anotherembodiment, the aerodynamic encasement can use position locating systemsof vehicles or transport systems to which the aerodynamic encasement isattached. Further, radiofrequency (RF) transmission of a known positionand triangulation/trilateration can be used in other embodiments. Forexample, the aerodynamic encasement 100 could be resting within aground-based landing and takeoff depot that is designed, at least inpart, to store the aerodynamic encasements 100 of the present invention.Such depots contain a plurality of beacons, the precise locations ofwhich are known and fixed. In this circumstance, the aerodynamicencasement 100 can determine its precise location via short-rangebeacons communicating with the depot beacons, using thistriangulation/trilateration approach.

In one or more embodiments, the aerodynamic encasement 100 may alsoinclude a system to assist a UAV to determine its precise locationand/or orientation to enable the aircraft to align with the aerodynamicencasement 100 so that it can be properly coupled to the UAV. Forexample, visual and similar marker-based systems can be incorporatedonto the exterior of the aerodynamic encasement 100 to aid in preciselocating and positioning. As a UAV approaches the aerodynamic encasement100 for retrieval or positioning, markers placed at key locations on theaerodynamic encasement 100 can aid external systems to preciselydetermine the aerodynamic encasement's location and orientation as anaid to navigation and alignment.

In one or more embodiments, the aerodynamic encasement 100 of thepresent invention can also include the ability to communicate to otherdevices wirelessly via several optionally-populated transceivers,including one or more of 802.11 (i.e. “Wi-Fi”), cellular data networks(e.g. “3G”, “4G/LTE”, etc.), satellite communications (e.g. Iridium),point-to-point radio (RF) modems, mesh-networked radio (RF) modems,Bluetooth, and the like. These communication devices can be encasedwithin the body of the aerodynamic encasement 100 and optionally withinan epoxy mass that is attached to the fairing 116 of the aerodynamicencasement 100. Encasing these devices in this way protects them fromweather elements, accidental strikes, and theft. Additionally, customenclosures or enclosures adapted from other purposes might serve toaffix communication devices to the aerodynamic encasement 100 andshelter them from the elements.

In an embodiment, the aerodynamic encasement 100 transmits data relatingto its identification, location, cargo load status and/or orientationvia the internet to many possible locations, including to a centralserver, to other connected aerodynamic encasements, to aircraft andtransport systems, to ground control, to ground staff, and to monitoringsystems, automated planning systems, UAVs, etc. In another embodiment,the aerodynamic encasement 100 can monitor and report its load capacity.As various components are added or removed, the aerodynamic encasement's100 cargo arrangement can be optimized for transport. Moreover, thecommunication system described above can be used to enable a “chain ofcustody”. For example, one party could be delivering a certainaerodynamic encasement 100 via an aircraft, a second party could be theowner of cargo in that aerodynamic encasement 100, and a third partycould be ready to accept delivery of that aerodynamic encasement 100. Asthe aircraft carrying the aerodynamic encasement 100 approaches itsdestination, sending its location to a server, the server could informthe third party to be ready to accept delivery. Then once the aircraftlands, the third party could accept the delivery, confirming itsacceptance electronically with the server, at which time the serverinforms the aircraft or the first party as well as the aerodynamicencasement owner (the second party) that the aerodynamic encasement 100has been accepted. In some embodiments of the present invention, thethird-party is a depot as discussed earlier.

In one or more embodiments, as schematically illustrated in FIG. 21, anonboard battery pack provides electrical power for the aerodynamicencasement's 100 onboard devices. The battery can be charged in severalpossible ways, including a photovoltaic (“solar power”) cell that ismounted on top of the aerodynamic encasement or is incorporated into theexternal composite skin of the aerodynamic encasement, a powerconnection to the UAV that is connected upon pick-up and engagement withthe UAV, and/or a shore-power connection that is connected to groundinfrastructure. As illustrated in FIG. 21, the aerodynamic encasement100 of the present invention can also incorporate a climate control unit(i.e. temperature control system) for climate-sensitive cargo. Aprocessing unit with a temperature probe placed within the aerodynamicencasement 100 near climate-sensitive cargo informs a software systemmanaging heating and cooling devices within the aerodynamic encasement100 to maintain a preset temperature range. The processor is alsocapable of logging the time-history of temperatures while the cargo isin the aerodynamic encasement 100, providing an auditable temperaturehistory of the cargo for example for “cold chain” applications. Othersensors are also contemplated. Data with respect to sensors incorporatedwithin, or associated with, the aerodynamic encasement 100 can betransferred to the UAV via hardline cable or wirelessly. In yet anotherembodiment, as schematically illustrated in FIG. 22, the processing unitcommands a sprayer unit to spray liquid from the aerodynamic encasement100. The sprayer unit consists of a liquid supply tank, a pump, anozzle, and piping. The unit is commanded to spray liquids over certainareas in-flight. The liquid could be water (for e.g. firefighting),flame retardant, fertilizer (for e.g. farming) or pesticide, amongothers.

In one or more embodiments, the aerodynamic encasement 100 includes theability to detach from the aerial vehicle during flight in instances ofemergency or, in other situations, in which landing the aircraft (UAV)is not feasible, detach and deploy a parachute. In yet another scenariothe aerodynamic encasement 100 is able to be lowered from the hoveringaircraft at a height and released so that the aircraft would not have toland to release the aerodynamic encasement 100. For this purpose, theaerodynamic encasement 100 may include a parachute system (now shown)that enables the aerodynamic encasement 100 to fall at a safe velocityif detached from the UAV mid-flight. The parachute can either bedeployed via the use of a pull-cord attached to the UAV or via anonboard system that triggers parachute deployment (via e.g. aservo-actuator or pyrotechnic charge). The onboard system can beprogrammed to deploy the parachute either automatically (using e.g.onboard inertial sensors to detect freefall or barometric pressuresensors to determine altitude above mean sea level) or via a wirelesscommunication device in communication with the UAV or ground controlinfrastructure. Similarly, the aerodynamic encasement 100 can beconfigured to carry water or a fire retardant that can be dumped/vented.In this type of configuration, the UAV can be piloted into austereconditions inaccessible by manned aircraft in support of groundpersonnel.

In addition, the aerodynamic encasement 100 of the present invention canincorporate other sensors that measure various aspects of theoperational state the aerodynamic encasement 100 itself. For example,the aerodynamic encasement 100 can include inertial, barometricpressure, or magnetic sensors that enable the aerodynamic encasement 100to measure its state of movement, orientation, altitude, and/or magneticheading; Internal proximity or imaging sensors (e.g., sonar,time-of-flight, infrared, cameras, etc.) that, together with software,enable the aerodynamic encasement 100 to determine the amount, size ortype of payload in the cargo area thereof, occupied volume, remainingcapacity, etc.; force or pressure transducers at the points of groundcontact that measure the aerodynamic encasement's 100 current overallweight and weight distribution; electrical sensors that measure thestate of charge, voltage, current, and power of the aerodynamicencasement's 100 battery and/or battery charging system; and;temperature and relative humidity sensors that measure the ambientatmospheric conditions inside and/or outside the aerodynamic encasement100; time-of-flight, beacon, or ranging sensors that enable theaerodynamic encasement's 100 location and orientation relative to theUAV to be determined with sufficient accuracy to enable navigation ofthe UAV to the aerodynamic encasement 100 for pickup.; visual markers,recognizable patterns or logos, or fiducials that can be located bycamera(s) on-board the UAV, to enable the UAV to determine theaerodynamic encasement's 100 location and orientation with sufficientaccuracy for the UAV to navigate to the aerodynamic encasement 100 forpickup; retroreflective patterned surfaces on the aerodynamic encasement100 that enable a scanning laser rangefinder (“LIDAR”) on-board the UAVto determine the aerodynamic encasement's 100 location and orientationwith sufficient accuracy for the UAV to navigate to the aerodynamicencasement 100 for pickup; multiple precise satellite-based positioningsystem modules positioned to enable the determination ofheading/orientation; and the like.

The present description relates to the method for modular aviation cargotransport as described above. The various embodiments and variantsdisclosed above apply mutatis mutandis to the method for modularaviation cargo transport. FIG. 23 provides a flowchart 200 listing stepsinvolved in the method for modular aviation cargo transport. At step202, the method includes loading a platform (such as, the platform 106)with cargo, the platform 106 having a planar upper surface 108configured to accept the cargo and a lower surface 110 wherein the lowersurface 110 includes two or more ground supports 112 displacing aportion of the platform 106 from contact with a supporting surface andwherein the platform 106 includes two or more load transfer structures132. At step 204, the method includes encasing the platform 106 with afairing (such as, the fairing 116), the fairing 116 configured todetachably couple to the platform 106 wherein the fairing 116, whencoupled to the platform 106, forms an aerodynamic encasement. At step206, the method includes detachably mounting the aerodynamic encasementto an aircraft by the two or more load transfer structures 132.

The method further includes displacing, by the ground supports 112, thelower surface 110 of the platform 106 away the supporting surfacesufficient to accept a lifting mechanism (such as, the lifting mechanism114). The method further includes accepting, by the two or more loadtransfer structures 132, a grasping mechanism wherein the graspingmechanism is configured to raise the aerodynamic encasement to theaircraft. The method further includes mounting the aerodynamicencasement to the aircraft. Herein, the fairing 116 includes a frontportion 118 and a rear portion 120, and the method further includesjoining the front portion 118 to the rear portion 120 to encase theplatform 106. Responsive to joining the front portion 118 and the rearportion 120, the method further includes coupling the fairing 116 to theplatform 106. Herein, the lower surface 110 of the platform 106 forms anexterior surface of the aerodynamic encasement. Further, the fairing 116is a singular component configured to cover the platform 106. The methodfurther includes detaching a detachable side panel (such as, thedetachable side panel 140) from the fairing 116. The method furtherincludes laterally accepting the platform 106 into the fairing 116 andreattaching the detachable side panel 140 to form the aerodynamicencasement.

The aerodynamic encasement 100 of the present invention can accept aload from any direction (except from below) that stands off the groundenough to accept the tines of a pallet jack for loading of the cargotherefrom. After loading, the aerodynamic encasement 100 is formed byfitting a fairing over the platform. Thereafter, the aerodynamicencasement 100 is attached to an aircraft by means as discussed. Theaerodynamic encasement 100 of the present invention has a fully enclosedform with flat bottom (having, in one embodiment, a dimension of about24 inches by 72 inches, for example) such that in can be repositionedwith a pallet jack if required and loaded as a unit into an intermodalcontainer. The modular nature of the aerodynamic encasement 100 enablescargo to be quickly loaded and unloaded in its non-encased state and yetswiftly attached to an aircraft for transportation and deployment.

While there have been described above the principles of the presentinvention in conjunction with an aviation cargo aerodynamic encasementand a method for modular aviation cargo transport, it is to be clearlyunderstood that the foregoing description is made only by way of exampleand not as a limitation to the scope of the invention. Particularly, itis recognized that the teachings of the foregoing disclosure willsuggest other modifications to those persons skilled in the relevantart. Such modifications may involve other features that are alreadyknown per se and which may be used instead of or in addition to featuresalready described herein. Although claims have been formulated in thisapplication to particular combinations of features, it should beunderstood that the scope of the disclosure herein also includes anynovel feature or any novel combination of features disclosed eitherexplicitly or implicitly or any generalization or modification thereofwhich would be apparent to persons skilled in the relevant art, whetheror not such relates to the same invention as presently claimed in anyclaim and whether or not it mitigates any or all of the same technicalproblems as confronted by the present invention. The Applicant herebyreserves the right to formulate new claims to such features and/orcombinations of such features during the prosecution of the presentapplication or of any further application derived therefrom.

The foregoing descriptions of specific embodiments of the presentdisclosure have been presented for purposes of illustration anddescription. They are not intended to be exhaustive or to limit thepresent disclosure to the precise forms disclosed, and obviously manymodifications and variations are possible in light of the aboveteaching. The exemplary embodiment was chosen and described in order tobest explain the principles of the present disclosure and its practicalapplication, to thereby enable others skilled in the art to best utilizethe present disclosure and various embodiments with variousmodifications as are suited to the particular use contemplated.

1. A modular aerodynamic cargo encasement, comprising: a platform havinga planar upper surface configured to accept cargo and a lower surface,wherein the lower surface includes two or more ground supportsdisplacing a portion of the platform from contact with a supportingsurface, the platform having two or more load transfer structures; and afairing configured to detachably couple to the platform, wherein thefairing includes a front portion and a rear portion, wherein the frontportion couples with the rear portion forming a singular component andwhen coupled to the platform forms an aerodynamic encasement, andwherein the aerodynamic encasement is detachably mountable to anaircraft by the two or more load transfer structures.
 2. The modularaerodynamic cargo encasement of claim 1, wherein the ground supports areconfigured to displace the lower surface of the platform away thesupporting surface sufficient to accept a lifting mechanism.
 3. Themodular aerodynamic cargo encasement of claim 1, wherein the planarupper surface includes a plurality of tie down fixtures.
 4. The modularaerodynamic cargo encasement of claim 1, wherein the two or more groundsupports are aerodynamically shaped.
 5. The modular aerodynamic cargoencasement of claim 1, wherein the two or more load transfer structuresinclude a guide configured to accept a grasping mechanism.
 6. Themodular aerodynamic cargo encasement of claim 5, wherein the graspingmechanism is configured to raise the aerodynamic encasement to theaircraft whereby the aerodynamic encasement is mounted to the aircraft.7. The modular aerodynamic cargo encasement of claim 1, wherein theplatform includes a honeycomb structure.
 8. The modular aerodynamiccargo encasement of claim 1, wherein the platform includes a corrugatedstructure.
 9. The modular aerodynamic cargo encasement of claim 1,wherein the lower surface of the platform forms an exterior surface ofthe aerodynamic encasement.
 10. The modular aerodynamic cargo encasementof claim 1, wherein the fairing is configured to withstand aerodynamicforces exerted on the aerodynamic encasement up to 300 mph.
 11. Themodular aerodynamic cargo encasement of claim 1, wherein the rearportion includes a detachable side panel configured to laterally acceptthe platform to form the aerodynamic encasement.
 12. The modularaerodynamic cargo encasement of claim 1, wherein the rear portionincludes a pivotable side panel configured to laterally accept theplatform to form the aerodynamic encasement.
 13. A method for modularaerial cargo transport, comprising: loading a platform with cargo, theplatform having a planar upper surface configured to accept the cargoand a lower surface wherein the lower surface includes two or moreground supports displacing a portion of the platform from contact with asupporting surface and wherein the platform includes two or more loadtransfer structures; encasing the platform with a fairing wherein thefairing includes a front portion and a rear portion and wherein thefront portion couples with the rear portion forming a singular componentcovering the platform, the fairing configured to detachably couple tothe platform and wherein the fairing, when coupled to the platform,forms an aerodynamic encasement; and detachably mounting the aerodynamicencasement to an exterior of an aircraft by the two or more loadtransfer structures.
 14. The method for modular aerial cargo transportaccording to claim 13, further comprising displacing, by the groundsupports, the lower surface of the platform away the supporting surfacesufficient to accept a lifting mechanism.
 15. The method for modularaerial cargo transport according to claim 14, further comprisingaccepting, by the two or more load transfer structures, a graspingmechanism wherein the grasping mechanism is configured to raise theaerodynamic encasement to the aircraft.
 16. The method for modularaerial cargo transport according to claim 15, further comprisingmounting the aerodynamic encasement to the aircraft.
 17. The method formodular aerial cargo transport according to claim 13, further comprisingjoining the front portion to the rear portion to encase the platform.18. The method for modular aerial cargo transport according to claim 17,responsive to joining the front portion and the rear portion, furthercomprising coupling the fairing to the platform.
 19. The method formodular aviation cargo transport according to claim 13, furthercomprising, forming by the lower surface of the platform an exteriorsurface of the aerodynamic encasement.
 20. The method for modular aerialcargo transport according to claim 13, further comprising detaching adetachable side panel from the fairing.
 21. The method for modularaerial cargo transport according to claim 20, further comprisinglaterally accepting the platform into the fairing and reattaching thedetachable side panel to form the aerodynamic encasement.